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对一种腹下后置大偏距S弯进气道进行高速风洞试验研究,得到了该进气道的工作特性:(1)随着流量系数的增加,进气道出口总压恢复系数略有下降,稳态周向畸变指数、紊流度和综合畸变指数均上升;当流量系数较大或较小时,进气道出口气流总压脉动均存在局部峰值。(2)在试验研究范围内,来流马赫数和侧滑角的变化对进气道性能影响不大;随着迎角的增大,总压恢复系数有所上升,畸变指数有所下降。(3)进/发匹配点处,进气道出口气流总压脉动功率谱密度分布呈现白噪声特征,对进气道/发动机匹配工作是有利的。
A high-speed wind tunnel test was conducted on a high-speed wind tunnel with a large offset S-bellow at the rear of the abdomen. The operating characteristics of the inlet were obtained: (1) With the increase of the flow coefficient, the total outlet pressure recovery coefficient Slightly decreased, steady state circumferential distortion index, turbulence and comprehensive distortion index increased; when the flow coefficient is larger or smaller, there is a local peak in the total pressure pulsation of the inlet airflow. (2) Within the range of experimental study, the changes of Mach number and side slip angle have little effect on the inlet port performance. As the angle of attack increases, the total pressure recovery coefficient increases and the distortion index decreases. (3) At the entry / exit matching point, the power spectral density distribution of the total pressure pulsation in the outlet airway presents a white noise characteristic, which is beneficial to the inlet / engine matching work.